CN102230765B - Longitudinal unfolding mechanism for direct-connected folding wing - Google Patents
Longitudinal unfolding mechanism for direct-connected folding wing Download PDFInfo
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- CN102230765B CN102230765B CN 201110138539 CN201110138539A CN102230765B CN 102230765 B CN102230765 B CN 102230765B CN 201110138539 CN201110138539 CN 201110138539 CN 201110138539 A CN201110138539 A CN 201110138539A CN 102230765 B CN102230765 B CN 102230765B
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- cam
- conduit
- guide rail
- wing
- missile wing
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Abstract
The invention relates to a longitudinal unfolding mechanism for a direct-connected folding wing. At present, folding wings of all missiles have functions of one time unfolding and locking, and the unfolding time of the folding wings of all the missiles is very short, the unfolding and locking impact is higher, and the interference on the posture of a flying missile is higher. By adoption of a direct-connected cam mechanism design idea, the reliable locking of folding wings of the missiles can be realized at a time. Power is supplied by a gas actuator cylinder and directly drives a cam to movealong a guide rail; and a driven sliding block on the missile wing is contacted with a chute of the cam and moves in the chute of the cam to realize unfolding of the folding wing. By the longitudinalunfolding mechanism, the minimization of a wrapping space of the folding wing is realized, the mechanism is compact, and high-precision and high-reliability folding, unfolding and locking can be realized easily.
Description
Technical field
The present invention relates to a kind of folding wings development mechanism with auto-lock function, can be applicable to the Deployment and locking of tactical missile folding wing.
Background technology
The guided missile missile wing is the important component part of body, and simple and convenient for guided missile launcher miniaturization, transportation are stored, tactical missile extensively adopts folding wings, to be launched after, again folding wings is launched, reach state of flight.The folding wings development mechanism is used for realizing the folding and expanding function of missile airfoil.The present domestic Missile Folding wing all has disposable expansion lock function, its duration of run is very short, launches the locking impact larger, and is larger to the body attitude disturbance, launch locking and impact even may cause locking pin to be cut off, make the missile wing can't locking positioning and cause catastrophic failure.
Summary of the invention
The objective of the invention is to realize that the Missile Folding wing is in the disposable locking that launches extreme position, and reduce the impact acceleration that body is caused, and then avoid being cut off because of locking pin missile wing can't normally be located, with the fast reserve that improves guided missile and the accuracy that strikes target.
Main design of the present invention: for reducing the enveloping space of the Missile Folding wing, adopt direct-connected Cam Design thought, realize the disposable positive lock of the Missile Folding wing.Power is moved along guide rail by the direct driving cam of combustion gas pressurized strut, and the driven sliding block on the missile wing contacts with the cam conduit, and along the mobile expansion that realizes folding wings in the cam conduit.The complete positive lock of folding wings then utilizes the locking pin on the driven sliding block to enter cam conduit pin-and-hole and realizes.
The technical solution adopted in the present invention is as follows:
Longitudinal unfolding mechanism for direct-connected folding wing comprises combustion gas pressurized strut, push rod, cam, guide rail and a pair of missile wing.Slide block in the combustion gas pressurized strut is fixedly connected with an end of push rod, and the other end of push rod is fixedly connected with cam, and cam can move up and down along guide rail, and the both sides of cam are provided with missile wing, are provided with the guide rail locking pin on the guide rail.
Described cam both sides have the cam conduit along the center line symmetry of cam, and the cam conduit is near having conduit locking pin-and-hole on the position of cam bottom; The centerline on the top of cam has the camlock pin-and-hole, and the camlock pin-and-hole can cooperate with the guide rail locking pin.
Described missile wing is provided with driven sliding block corresponding to cam conduit position, and this driven sliding block can be slided at the cam conduit, is provided with the slider locking pin on the driven sliding block.
So that missile wing rotates around the missile wing rotating shaft, its left missile wing clockwise rotates the fixed corresponding conduit locking of the slider locking lock on missile wing pin-and-hole after 90 ° to cam along the movement on the guide rail direction; Right missile wing rotates counterclockwise the fixed corresponding conduit locking of the slider locking lock on missile wing pin-and-hole after 90 °; The upper limit position that cam moves is determined by camlock pin-and-hole and guide rail locking pin.
The present invention compared with prior art has following beneficial effect: 1, the direct-connected Combination application of cam mechanism and slide block mechanism takes full advantage of the joint space of folding wings, has satisfied envelope minimized in size principle; 2, the accurate positioning of development mechanism, load are good, can guarantee fast, stable, in time, accurately launch; 3, guide rail locking pin, driven sliding block locking pin and pin-and-hole be equipped with accurate location and reliable locking when having guaranteed that missile wing forwards predetermined angular to, and bomb body is disturbed little, be conducive to keep the stability of missile flight attitude; 4, adopt double-vane to be arranged symmetrically with longitudinal folding mode, realized the maximization of folding wings developed area, improved the flight lift of guided missile; 5, applied range.The present invention also can be applicable to the collapsible sun wing, deployable antenna, on the space development mechanisms such as the space mast ground mechanism relevant with other except can being installed in folding wings folding exhibition joint.
Description of drawings
Fig. 1 is folded state schematic diagram of the present invention;
Fig. 2 is deployed condition schematic diagram of the present invention.
The specific embodiment
The invention will be further described below in conjunction with accompanying drawing.
Longitudinal unfolding mechanism for direct-connected folding wing comprises that combustion gas pressurized strut 1(provides power source); Missile wing 2,16; Conduit locking pin hole 3,15(cooperate with the slider locking pin in the cam, are used for the positioning and locking that missile wing launches the ultimate position); Cam 4; Missile wing gyroaxis 5,14; Cam conduit 6,13(contact with driven sliding block); Camlock pin-and-hole 7(cooperates with the guide rail locking pin, is used for location, the locking of cam); Missile wing driven sliding block 8,12(drive missile wing and rotate); Slider locking pin 9,11(are embedded in the slide block in advance); Locking pin 10(is fixed on the guide rail); Guide rail 17; Push rod 18(actuating cam is along guide rail movement).Slide block in the described combustion gas pressurized strut 1 is fixedly connected with an end of push rod 18, and the other end of push rod 18 is fixedly connected with cam 4, and cam 4 can move along guide rail 17, the both sides of cam 4 are provided with missile wing 2,16, its left missile wing is 2, and right missile wing is 16, is provided with guide rail locking pin 10 on the guide rail 17.
Described cam 4 both sides have the cam conduit along the center line symmetry of cam 4 and are respectively 6,13, its left cam path road is 6, right cam conduit is 13, left cam conduit 6 is near having left conduit locking pin-and-hole 3 on the position of cam 4 bottoms, right cam conduit 13 is near having right conduit locking pin-and-hole 15 on the position of cam 4 bottoms, the centerline on the top of cam 4 has camlock pin-and-hole 7, and camlock pin-and-hole 7 can cooperate with guide rail locking pin 10.
Described left missile wing 2 is provided with left driven sliding block 8 corresponding to left cam conduit 6 positions, and this driven sliding block 8 can in left cam conduit 6 interior slips, be provided with left slider locking pin 9 on the left driven sliding block 8; Right missile wing 16 is provided with right driven sliding block 12 corresponding to right cam conduit 13 positions, and this driven sliding block 12 can in right cam conduit 13 interior slips, be provided with right slider locking pin 11 on the right driven sliding block 12;
Combustion gas pressurized strut 1 makes cam 4 move along guide rail 17 by push rod 18, left driven sliding block 8 on the left missile wing 2 contacts with left cam conduit 6, thereby driving left driven sliding block 8 by cam 4 moves so that left missile wing 2 rotates around left missile wing rotating shaft 5 along left cam conduit 6 in the cam, after its left missile wing 2 clockwise rotates 90 °, left cam conduit locking pin hole 3 in the left conduit 6 of left slider locking pin 9 on the left missile wing 2 and cam cooperates, realizes that left missile wing 2 locks; Right driven sliding block 12 on the right missile wing 16 contacts with right cam conduit 13 simultaneously, thereby driving right driven sliding block 12 by cam 4 moves so that right missile wing 16 rotates around right missile wing rotating shaft 14 along right cam conduit 13 in the cam, after its right missile wing 16 rotates counterclockwise 90 °, right cam conduit locking pin hole 15 in the right conduit 13 of right slider locking pin 11 on the right missile wing 16 and cam cooperates, realize right missile wing 16 lockings, for guaranteeing that folding and expanding mechanism accurately puts in place, being provided with locking pin 10 on the guide rail cooperates with camlock pin-and-hole 7, guarantee the left folding wing 2, the reliable redundant locking of the right folding wing 16, thus finished left missile wing 2 and right missile wing 16 from folded state (such as Fig. 1) to deployed condition (such as Fig. 2).
Operation principle of the present invention is: longitudinal unfolding mechanism for direct-connected folding wing realizes that disposable reliably the expansion fully of folding wings locks, concrete principle is: combustion gas pressurized strut driving cam moves along guide rail, driven sliding block on the missile wing contacts with the cam conduit, move along conduit in the cam by the cam driven driven sliding block, thereby missile wing is rotated around its gyroaxis, namely realized the expansion of folding wings, and the locking pin on the driven sliding block enters in the cam conduit pin-and-hole and finishes the folding wings locking.Simultaneously, accurately put in place for guaranteeing folding and expanding mechanism, be provided with locking pin on the guide rail and cooperate with the camlock pin-and-hole, realize the safe, reliable of folding wings expansion extreme position, redundant location.Direct-connected folding wings development mechanism is simple in structure, compact, and power shaft and output shaft are arranged vertically, accurate positioning, reliable lock, bomb body is disturbed little, is conducive to keep in the missile flight process holding position, satisfy fast, stable, launch requirement timely.
Claims (1)
1. longitudinal unfolding mechanism for direct-connected folding wing comprises combustion gas pressurized strut, push rod, cam, guide rail and a pair of missile wing, it is characterized in that:
Slide block in the combustion gas pressurized strut is fixedly connected with an end of push rod, and the other end of push rod is fixedly connected with cam, and cam can move up and down along guide rail, and the both sides of cam are provided with missile wing, are provided with the guide rail locking pin on the guide rail;
Described cam both sides have the cam conduit along the center line symmetry of cam, and the cam conduit is near having conduit locking pin-and-hole on the position of cam bottom; The centerline on the top of cam has the camlock pin-and-hole, and the camlock pin-and-hole can cooperate with the guide rail locking pin;
Described missile wing is provided with driven sliding block corresponding to cam conduit position, and this driven sliding block can be slided at the cam conduit, is provided with the slider locking pin on the driven sliding block;
So that missile wing rotates around the missile wing rotating shaft, its left missile wing clockwise rotates the fixed corresponding conduit locking of the slider locking lock on missile wing pin-and-hole after 90 ° to cam along the movement on the guide rail direction; Right missile wing rotates counterclockwise the fixed corresponding conduit locking of the slider locking lock on missile wing pin-and-hole after 90 °; The upper limit position that cam moves is determined by camlock pin-and-hole and guide rail locking pin.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110138539 CN102230765B (en) | 2011-05-26 | 2011-05-26 | Longitudinal unfolding mechanism for direct-connected folding wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110138539 CN102230765B (en) | 2011-05-26 | 2011-05-26 | Longitudinal unfolding mechanism for direct-connected folding wing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102230765A CN102230765A (en) | 2011-11-02 |
| CN102230765B true CN102230765B (en) | 2013-10-16 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201110138539 Expired - Fee Related CN102230765B (en) | 2011-05-26 | 2011-05-26 | Longitudinal unfolding mechanism for direct-connected folding wing |
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| CN (1) | CN102230765B (en) |
Families Citing this family (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103123292B (en) * | 2013-01-07 | 2015-07-08 | 西北工业大学 | Folding wings pneumatic loading unfolding experiment device |
| US9012825B2 (en) * | 2013-01-23 | 2015-04-21 | Simmonds Precision Products, Inc. | Systems and methods for retaining and deploying canards |
| IL231186A (en) | 2014-02-26 | 2017-07-31 | Israel Aerospace Ind Ltd | Fin deployment system |
| CN104089546B (en) * | 2014-04-29 | 2015-09-30 | 北京理工大学 | The variable aerodynamic arrangement structure of body |
| CN104457443A (en) * | 2014-11-24 | 2015-03-25 | 江西洪都航空工业集团有限责任公司 | Up-down loading device for stacked folding wings |
| CN104713426B (en) * | 2015-04-01 | 2016-05-11 | 湖北航天技术研究院总体设计所 | The laterally folded aerofoil of a kind of sliding wedge formula |
| CN105737685B (en) * | 2016-02-18 | 2017-07-21 | 江西洪都航空工业集团有限责任公司 | A kind of two-way dibit foldable structure of aerofoil |
| CN106347632B (en) * | 2016-10-26 | 2018-10-26 | 中国科学院长春光学精密机械与物理研究所 | A kind of expansion retaining mechanism |
| CN109638405B (en) * | 2018-12-03 | 2020-07-17 | 南京航空航天大学 | High-precision multi-butt-joint locking surface antenna auxiliary unfolding mechanism |
| CN109539901B (en) * | 2018-12-25 | 2021-05-04 | 北京航天飞腾装备技术有限责任公司 | Outer folding wing system of cabin of big aspect ratio |
| CN109630541B (en) * | 2019-01-23 | 2023-08-04 | 黑龙江省科学院自动化研究所 | Rotatory folding aggregate unit of solar cell panel |
| CN114777574A (en) * | 2022-04-02 | 2022-07-22 | 合肥工业大学 | Folding missile wing device |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| AU5616086A (en) * | 1985-08-12 | 1987-02-19 | Grumman Aerospace Corporation | Penguin missile folding wing configuration |
| CN202126218U (en) * | 2011-05-26 | 2012-01-25 | 浙江理工大学 | Directly-connected lengthways unfolding mechanism for folding wings |
-
2011
- 2011-05-26 CN CN 201110138539 patent/CN102230765B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| AU5616086A (en) * | 1985-08-12 | 1987-02-19 | Grumman Aerospace Corporation | Penguin missile folding wing configuration |
| EP0214888A3 (en) * | 1985-08-12 | 1987-11-11 | Grumman Aerospace Corporation | Missile folding wing configuration |
| US4717093A (en) * | 1985-08-12 | 1988-01-05 | Grumman Aerospace Corporation | Penguin missile folding wing configuration |
| EP0214888B1 (en) * | 1985-08-12 | 1992-04-29 | Grumman Aerospace Corporation | Missile folding wing configuration |
| CN202126218U (en) * | 2011-05-26 | 2012-01-25 | 浙江理工大学 | Directly-connected lengthways unfolding mechanism for folding wings |
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| Publication number | Publication date |
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| CN102230765A (en) | 2011-11-02 |
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Granted publication date: 20131016 Termination date: 20180526 |